WO2019087389A1 - Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge - Google Patents

Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge Download PDF

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Publication number
WO2019087389A1
WO2019087389A1 PCT/JP2017/039916 JP2017039916W WO2019087389A1 WO 2019087389 A1 WO2019087389 A1 WO 2019087389A1 JP 2017039916 W JP2017039916 W JP 2017039916W WO 2019087389 A1 WO2019087389 A1 WO 2019087389A1
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WO
WIPO (PCT)
Prior art keywords
wing
shroud cover
centrifugal compressor
wings
edge
Prior art date
Application number
PCT/JP2017/039916
Other languages
English (en)
Japanese (ja)
Inventor
健一郎 岩切
良洋 林
茨木　誠一
Original Assignee
三菱重工エンジン＆ターボチャージャ株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 三菱重工エンジン＆ターボチャージャ株式会社 filed Critical 三菱重工エンジン＆ターボチャージャ株式会社
Priority to US16/609,645 priority Critical patent/US11313379B2/en
Priority to JP2019550122A priority patent/JP6902615B2/ja
Priority to CN201780091339.9A priority patent/CN110678658B/zh
Priority to EP17930344.1A priority patent/EP3708847B1/fr
Priority to PCT/JP2017/039916 priority patent/WO2019087389A1/fr
Publication of WO2019087389A1 publication Critical patent/WO2019087389A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Definitions

  • the present disclosure relates to a centrifugal compressor and a turbocharger provided with the centrifugal compressor.
  • centrifugal compressors There are two types of centrifugal compressors: a closed type in which the entire wing is covered by a shroud cover, and an open type in which the wing is not covered by a shroud cover.
  • Patent Documents 1 to 3 describe a centrifugal compressor in which a blade is covered by a shroud cover partially in the rotational axis direction of the impeller, for example, on the front edge side of the blade.
  • the shroud cover provided in the centrifugal compressors of Patent Documents 1 to 3 has a cylindrical shape having a certain shape along the circumferential direction of the shroud cover. While covering the blade with such a shroud cover has the effect of reducing the occurrence of clearance flow, there are also some disadvantages, but the conventional cylindrical shroud cover addresses these disadvantages. There was a problem that it was impossible.
  • At least one embodiment of the present disclosure is a centrifugal compressor in which a blade is partially covered by a shroud cover in the rotational axis direction of the impeller, and the disadvantage caused by providing the shroud cover
  • An object of the present invention is to provide a centrifugal compressor which can be reduced and a turbocharger provided with the centrifugal compressor.
  • a centrifugal compressor according to at least one embodiment of the present disclosure, An impeller having a plurality of first wings and rotatably provided; A shroud cover partially provided on the front edge side of the first wing in the rotational axis direction of the impeller, the shroud cover mutually connecting the first wings adjacent in the circumferential direction;
  • the shroud cover has a shape in which the position in the rotation axis direction of at least one of the upstream end edge and the downstream end edge of the shroud cover changes along the circumferential direction of the shroud cover.
  • the shroud cover has a shape that can cope with the disadvantages that may occur due to the provision of the shroud cover, the disadvantages can be reduced.
  • the shroud cover has a portion connected to the pressure surface of the first wing and a portion connected to the suction surface of the first wing, respectively, from the leading edge to the trailing edge of the first wing. It is configured to be within 30% or less of the meridian plane length of one wing.
  • the clearance flow mainly occurs in the range of 30% or less of the meridional plane length of the first wing.
  • the generation of the clearance flow is reduced by the shroud cover provided in the range of 30% or less of the meridional plane length of the first wing from the front edge to the rear edge of the first wing can do.
  • one of a meridional plane length of a portion connected to the pressure side of the first wing and a meridional plane length of a portion connected to the suction side of the first wing is longer than the other. It is configured.
  • the primary eigenmode for vibration of the first wing is a mode in which a portion on the front edge side of the first wing vibrates, providing the shroud cover on the front edge side of the first wing is a vibrating portion To add to the mass, leading to a decrease in the eigenvalue.
  • the shroud cover since the shroud cover has a narrow portion in the rotational axis direction, the shroud cover has a narrower width in the rotational axis direction than in the circumferential direction. The mass can be reduced, as a result of which the vibrations of the wing can be reduced.
  • the clearance flow is generated from the pressure side of the first wing to the suction side.
  • the shroud cover is a part of the upstream end edge from a portion connected to the pressure surface of the first wing between the circumferentially adjacent first blades to a portion connected to the suction surface of the first wing Is positioned closer to the trailing edge of the first wing than the throat position.
  • Covering the blade with a shroud cover may reduce the flow rate by reducing the throat area. According to the configuration of the above (4), since the shroud cover can be provided while avoiding the throat position, it is possible to suppress the decrease in the flow rate.
  • the shroud cover has a front end of a portion connected to the pressure side of the first wing at the front edge of the first wing and a front end of a portion connected to the suction side of the first wing It is comprised so that it may be located in the trailing edge side of the said 1st wing rather than a throat position.
  • the impeller is circumferentially adjacent to a plurality of second wings having a front edge portion on the rear edge side of the front edge portion of the first wing and having a meridional length shorter than the first wing. Further comprising between the first wings to be fitted, The shroud cover interconnects the first wings adjacent to each other in the circumferential direction and the second wings between the first wings.
  • the vibration in the natural mode of the first wing can be reduced by connecting the first wing and the second wing having a different vibration mode from the first wing by the shroud cover it can.
  • a centrifugal compressor is An impeller rotatably provided, having a plurality of first wings and a plurality of second wings provided between the first wings circumferentially adjacent to each other; A shroud cover provided partially on the front edge side of the first wing in the rotational axis direction of the impeller;
  • the second wing has a leading edge on the trailing edge side of the leading edge of the first wing and has a meridional length shorter than that of the first wing,
  • the shroud cover interconnects the first wings adjacent to each other in the circumferential direction and the second wings between the first wings.
  • the vibration in the natural mode of the first wing can be reduced. it can.
  • a turbocharger according to at least one embodiment of the present disclosure is: The centrifugal compressor according to any one of the above (1) to (7) is provided.
  • the shroud cover has a shape that can cope with the disadvantages that may occur due to the provision of the shroud cover, the disadvantages can be reduced.
  • the shroud cover changes along the circumferential direction of the shroud cover in the rotational axis direction of at least one of the upstream end edge and the downstream end edge of the shroud cover.
  • Embodiment 1 is a partial cross-sectional view of a centrifugal compressor according to Embodiment 1 of the present disclosure. It is a graph which shows distribution of the clearance flow obtained by CFD analysis by the present inventors. It is a figure showing an example of the shroud cover provided in the centrifugal compressor concerning Embodiment 1 of this indication. It is a figure which shows another example of the shroud cover provided in the centrifugal compressor based on Embodiment 1 of this indication. It is a figure showing the shroud cover provided in the centrifugal compressor concerning Embodiment 2 of this indication. It is a figure showing the shroud cover provided in the centrifugal compressor concerning Embodiment 3 of this indication.
  • centrifugal compressor according to some embodiments of the present disclosure shown below will be described by taking a centrifugal compressor of a turbocharger as an example.
  • the centrifugal compressor in the present disclosure is not limited to a centrifugal compressor of a turbocharger, and may be any centrifugal compressor operating alone.
  • the fluid compressed by this compressor is air, but can be replaced by any fluid.
  • the centrifugal compressor 1 As shown in FIG. 1, the centrifugal compressor 1 according to the first embodiment includes a housing 2 and an impeller 3 rotatably provided around the rotational axis L in the housing 2.
  • the impeller 3 has a plurality of streamline-shaped first wings 4 (only one first wing 4 is drawn in FIG. 1) provided at predetermined intervals in the circumferential direction.
  • the impeller 3 is provided with an annular shroud cover 5 partially in the direction of the rotation axis L from the front edge 4 a to the rear edge 4 b of the first wing 4.
  • the shroud cover 5 mutually connects the outer peripheral edge portions 4c and 4c of the first wings 4 and 4 adjacent in the circumferential direction.
  • the range in which the shroud cover 5 is provided will be described.
  • the inventors conducted CFD analysis on a centrifugal compressor provided with an open type impeller in which a blade is not covered by a shroud cover, and determined a region where a clearance flow occurs.
  • the analysis result is shown in FIG. From this result, it was found that the clearance flow mainly occurs within 30% or less of the meridional plane length from the front edge 4a of the first wing 4 toward the rear edge 4b. Therefore, in order to reduce the occurrence of clearance flow, it is preferable to provide the shroud cover 5 within this range. Even if the shroud cover 5 is provided in the range on the rear edge 4 b side than this range, the effect of reducing the occurrence of the clearance flow is not improved.
  • the present inventors have also reported the results of CFD analysis for a closed-type centrifugal compressor (Ibaraki, S., Furukawa, M., Iwakiri, K. and Takahashi, K., Vertical flow structure and loss generation process in a transonic centrifugal compressor impeller, Proceedings of ASME Turbo Expo 2007, Montreal, Canada, GT 2007-27791 (2007)).
  • the closed type centrifugal compressor has an advantage that it is possible to suppress the generation of loss due to the clearance flow, but a scraping vortex in which low energy fluid accumulated on the trailing edge side of the wing is wound is generated There is a disadvantage that losses may occur due to
  • the first wing 4 is moved from the front edge 4 a of the first wing 4 toward the rear edge 4 b. While the occurrence of clearance flow can be reduced by the shroud cover 5 provided in the range of 30% or less of the meridian length of the above, the raking vortices are generated by the absence of the shroud cover on the rear edge 4b side of the first wing 4 It is possible to suppress the occurrence of loss due to the occurrence.
  • the primary eigenmode of the first wing 4 is a mode in which the leading edge 4a side is shaken, and in the centrifugal compressor 1, the mass of the shroud cover 5 is added to this portion, which leads to a decrease in the eigenvalue .
  • the shroud cover 5 provided in the centrifugal compressor 1 has a shape in which the position of the downstream end 5b in the rotational axis L direction changes along the circumferential direction of the shroud cover 5.
  • the rear end portion 11 b of the portion 11 connected to the pressure surface 4 d of the first wing 4 is connected to the suction surface 4 e of the first wing 4
  • the shape located closer to the front edge 4 a of the first wing 4 than the rear end 12 b of the portion 12, that is, the meridional length of the portion 11 connected to the pressure surface 4 d of the first wing 4 is It has a shape shorter than the meridional length of the portion 12 connected to the suction surface 4 e of the wing 4.
  • the rear end 12 b of the portion 12 connected to the negative pressure surface 4 e of the first wing 4 is on the pressure side 4 d of the first wing 4.
  • the shroud cover 5 shown in each of FIGS. 3 and 4 since there is a narrow portion in the direction of the rotation axis L (see FIG. 1) at the rear end 11b and the rear end 12b, the shroud cover In the case where the position of the downstream end 5b in the direction of the rotation axis L of the downstream side 5b is constant along the circumferential direction of the shroud cover 5, that is, the shroud cover is wider than in the case where the width in the rotation The mass of 5 can be reduced. As a result, the vibration of the first wing 4 can be reduced.
  • the clearance flow on the front edge 4a side of the first wing 4 occurs from the pressure side 4d to the suction side 4e. Therefore, in order to reduce the occurrence of the clearance flow, either the portion 11 connected to the pressure surface 4d or the portion 12 connected to the suction surface 4e goes from the front edge 4a to the rear edge 4b. It suffices to sufficiently cover the range of 30% or less of the meridional length of the first wing 4.
  • the shroud cover 5 shown in each of FIG. 3 and FIG. 4 reduces the vibration of the first wing 4 by reducing the mass of the shroud cover 5 since the portion 12 and the portion 11 respectively cover the entire range. While, the occurrence of the clearance flow can be reduced.
  • the shroud cover 5 has a shape in which the position of the downstream end 5b in the rotational axis L direction changes along the circumferential direction of the shroud cover 5, so that the width in the rotational axis L direction is Since there is a narrow portion, the shroud cover 5 has a shroud cover 5 compared to the case where the positions in the direction of the rotation axis L of the upstream end 5a and the downstream end 5b are constant along the circumferential direction of the shroud cover 5
  • the mass of 5 can be reduced, and as a result, the vibration of the first wing 4 can be reduced.
  • the shroud cover 5 has a meridional length of the portion 11 connected to the pressure side 4 d of the first wing 4 and a meridional length of the portion 12 connected to the negative pressure side 4 e of the first wing 4.
  • the shroud cover 5 has a point where the meridional length of the portion 11 connected to the pressure side 4 d of the first wing 4 is shorter than the meridional length of the portion 12 connected to the negative side 4 e of the first wing 4
  • the meridional plane length of the portion 12 connected to the negative pressure surface 4e of the first wing 4 includes both in the circumferential direction a location shorter than the meridional plane length of the portion 11 connected to the pressure side 4d of the first wing 4 It may be.
  • the entire shroud cover 5 is provided in a range of 30% or less of the meridional plane length of the first wing 4 from the front edge 4 a to the rear edge 4 b of the first wing 4. It is not limited to this form. It is sufficient if at least the portion 11 connected to the pressure surface 4 d of the first wing 4 and the portion 12 connected to the suction surface 4 e of the first wing 4 fall within this range. The part 5b may be out of this range.
  • the centrifugal compressor according to the second embodiment is the same as the first embodiment except that the shape of the shroud cover 5 is changed.
  • the same components as those of the first embodiment are denoted by the same reference numerals, and the detailed description thereof is omitted.
  • the shroud cover 5 has a shape in which the position of the upstream end 5 a in the rotational axis L direction changes along the circumferential direction of the shroud cover 5. Specifically, as shown in FIG. 5, in the shroud cover 5, the front end 12 a of the portion 12 connected to the negative pressure surface 4 e of the first wing 4 is connected to the positive pressure surface 4 d of the first wing 4 The front edge 11a of the portion 11 is located on the rear edge 4b side of the first wing 4 in the rotational axis L direction, and the rear edge 4b side of the first wing 4 in the rotational axis L direction than the throat position 10 It has a shape located at The other configuration is the same as that of the first embodiment.
  • Covering the first wing 4 with the shroud cover 5 can reduce the generation of the clearance flow as described above in the first embodiment, but the flow area may decrease due to the reduction of the throat area by the thickness of the shroud cover 5 There is a disadvantage that there is.
  • the shroud cover 5 can be provided while avoiding the throat position 10, a decrease in the flow rate can be suppressed.
  • the shroud cover 5 of the second embodiment has a shape in which the position of the upstream side edge portion 5 a in the direction of the rotation axis L changes along the circumferential direction of the shroud cover 5. Since a narrow portion is present, the vibration of the first wing 4 can also be reduced as in the first embodiment. Furthermore, in the shroud cover 5 of the second embodiment, the portion 11 connected to the pressure side 4d of the first wing 4 is 30% of the meridional plane length of the first wing 4 from the front edge 4a toward the rear edge 4b. Since the whole of the following range is covered, the occurrence of the clearance flow can also be reduced as in the first embodiment.
  • the entire upstream end 5a of the shroud cover 5 from the front end 11a to the front end 12a is located closer to the rear edge 4b of the first wing 4 in the rotational axis L direction than the throat position 10.
  • a portion of the upstream end 5a of the shroud cover 5 from the front end 11a to the front end 12a may be located closer to the rear edge 4b of the first wing 4 in the rotational axis L direction than the throat position 10.
  • the position of the downstream end 5b of the shroud cover 5 in the direction of the rotation axis L is constant in the circumferential direction, but the present invention is not limited to this.
  • the position of the downstream end 5b of the shroud cover 5 in the direction of the rotation axis L may also change in the circumferential direction. That is, the configuration of the shroud cover 5 of the first embodiment may be combined with the configuration of the shroud cover 5 of the second embodiment.
  • the centrifugal compressor according to the third embodiment is modified such that the impeller 3 has a second wing different in shape from the first wing 4 in addition to the first wing 4 for each of the first and second embodiments. It is in addition, although Embodiment 3 is described below in the form which changed the centrifugal compressor of Embodiment 1, it is also possible to change the centrifugal compressor of Embodiment 2 to the form of Embodiment 3.
  • FIG. In the third embodiment the same components as those of the first embodiment are denoted by the same reference numerals, and the detailed description thereof is omitted.
  • the impeller 3 is provided between a plurality of streamlined first wings 4 provided at predetermined intervals in the circumferential direction and the first wings 4 and 4 adjacent in the circumferential direction. And a plurality of splitter blades 20 which are the second wings.
  • the splitter blade 20 has a front edge 20 a on the rear edge 4 b side of the front edge 4 a of the first wing 4 and has a meridional length shorter than that of the first wing 4.
  • the shroud cover 5 interconnects the first blades 4 and 4 adjacent to each other in the circumferential direction with the splitter blade 20 between the first blades 4 and 4.
  • the shroud cover 5 has a shape in which the position of the downstream end 5b in the direction of the rotation axis L changes in the circumferential direction.
  • the other configuration is the same as that of the first embodiment.
  • the vibration of the first wing 4 in the eigenmode is reduced by connecting the first wing 4 and the splitter blade 20 having a vibration mode different from that of the first wing 4 by the shroud cover 5. be able to.
  • the portion 11 connected to the pressure side 4d of the first wing 4 is 30% of the meridional plane length of the first wing 4 from the front edge 4a toward the rear edge 4b. Since the following range is covered, the occurrence of clearance flow can also be reduced as in the first embodiment.
  • the rear end 12 b of the portion 12 connected to the suction surface 4 e of the first wing 4 is connected to the pressure surface 4 d of the first wing 4
  • the shape may be located closer to the front edge 4 a of the first wing 4 than the rear end 11 b of the portion 11.
  • the vibration of the first wing 4 can be reduced.
  • the portion 11 covers the entire range of 30% or less of the meridional length of the first wing 4 from the front edge 4a to the rear edge 4b, the clearance flow is the same as the shroud cover 5 of FIG. Can also be reduced.
  • the positions of the upstream end 5 a and the downstream end 5 b in the direction of the rotation axis L are the circumferential direction of the shroud cover 5.
  • the splitter blades 20 between the first wings 4 and 4 adjacent to each other in the circumferential direction may be connected to each other. Also in this case, since the first wing 4 and the splitter blade 20 having a vibration mode different from that of the first wing 4 are connected by the shroud cover 5, vibration in the natural mode of the first wing 4 can be reduced. it can.
  • centrifugal compressor 2 housing 3 impeller 4 first wing 4 a front edge 4 b (first wing) rear edge 4 c (first wing) outer edge 4 d (first wing) positive (first wing) positive Pressure surface 4e suction surface 5 (first blade) Shroud cover 5a upstream edge 5b (of shroud cover) downstream edge 10 (of shroud cover) Throat position 11 Part connected to pressure surface of first blade 11a (a portion connected to the pressure side of the first wing) 11b (a portion connected to the pressure side of the first wing) a rear end 12 portion 12a (connected to the suction side of the first wing) The front end 12b of the part connected to the suction surface of one wing The rear end 20 (of the part connected to the suction surface of the first wing) Splitter blade (second wing)

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

La présente invention concerne un compresseur centrifuge comprenant : un rouet ayant une pluralité de premières pales et conçu de façon à pouvoir se mettre en rotation ; et un revêtement de flasque disposé partiellement sur le côté de bord avant des premières pales dans la direction de l'axe de rotation du rouet, et raccordant les premières pales adjacentes entre elles dans la direction circonférentielle, le revêtement de flasque ayant une forme telle que la position, dans la direction de l'axe de rotation, du bord amont ou du bord aval du couvercle de flasque change le long de la direction circonférentielle du couvercle de flasque.
PCT/JP2017/039916 2017-11-06 2017-11-06 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge WO2019087389A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US16/609,645 US11313379B2 (en) 2017-11-06 2017-11-06 Centrifugal compressor and turbocharger including the same
JP2019550122A JP6902615B2 (ja) 2017-11-06 2017-11-06 遠心圧縮機及びこの遠心圧縮機を備えたターボチャージャ
CN201780091339.9A CN110678658B (zh) 2017-11-06 2017-11-06 离心压缩机以及具备该离心压缩机的涡轮增压器
EP17930344.1A EP3708847B1 (fr) 2017-11-06 2017-11-06 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge
PCT/JP2017/039916 WO2019087389A1 (fr) 2017-11-06 2017-11-06 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2017/039916 WO2019087389A1 (fr) 2017-11-06 2017-11-06 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge

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WO2019087389A1 true WO2019087389A1 (fr) 2019-05-09

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PCT/JP2017/039916 WO2019087389A1 (fr) 2017-11-06 2017-11-06 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge

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US (1) US11313379B2 (fr)
EP (1) EP3708847B1 (fr)
JP (1) JP6902615B2 (fr)
CN (1) CN110678658B (fr)
WO (1) WO2019087389A1 (fr)

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JPH06193594A (ja) 1992-10-17 1994-07-12 Asea Brown Boveri Ag 圧縮機の特性ダイアグラムを拡大するための安定化装置
JPH06235398A (ja) 1992-12-08 1994-08-23 Asea Brown Boveri Ag 圧縮機の特性線図を拡大するための安定化装置
JP2004353607A (ja) * 2003-05-30 2004-12-16 Mitsubishi Heavy Ind Ltd 遠心圧縮機
JP3653054B2 (ja) 2002-03-08 2005-05-25 三菱重工業株式会社 圧縮機のインペラーの構造
JP2010185456A (ja) * 2009-02-12 2010-08-26 Ebm - Papst Mulfingen Gmbh & Co Kg 遠心式送風機または斜流送風機に用いられるインペラ

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CN110678658A (zh) 2020-01-10
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CN110678658B (zh) 2022-03-04
US11313379B2 (en) 2022-04-26
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JPWO2019087389A1 (ja) 2020-04-09
US20200063749A1 (en) 2020-02-27

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